Aircraft electrostatic discharger layout design method

Abstract

The invention discloses a layout design method for an aircraft electrostatic discharger. The layout design method comprises the following steps: step 1, calculating and obtaining a total deposition electrostatic current of an aircraft; 2, calculating the number of electrostatic dischargers needing to be arranged on the aircraft according to the total deposition electrostatic current; 3, airplane deposition static electricity distribution simulation is carried out, and a final static electricity discharger arrangement area and the area number are determined; 4, according to the number of the electrostatic dischargers and the number of the areas, multiple initial layout schemes of the full-machine electrostatic dischargers are formed; 5, determining a layout design scheme of the full-machine electrostatic discharger by taking the maximum total discharge current IQ or balanced discharge of the full-machine electrostatic discharger as a judgment standard; and step 6, evaluating the rationality of the layout scheme of the whole-aircraft electrostatic discharger of the aircraft to obtain a final layout scheme of the whole-aircraft electrostatic discharger of the aircraft. According to the aircraft electrostatic discharger layout design method, balanced discharge or maximum deposition electrostatic discharge of a plurality of electrostatic dischargers can be realized.

Description

Technical Field

[0001] This invention belongs to the field of electromagnetic compatibility technology, specifically relating to a method for designing the layout of an aircraft electrostatic discharger. Background Technology

[0002] Aircraft electrostatic discharge (ESD) devices are used to discharge and control static charges accumulated during aircraft flight. Effective discharge by ESD devices is essential for aircraft electrostatic protection and electromagnetic compatibility (EMC) design. The placement of ESD devices on aircraft has long relied on engineering experience, typically involving multiple devices spaced 300 mm or more at the trailing edge of the wing. The aircraft's shape directly affects the overall static charge distribution and the electric field strength distribution at the device tips, thus influencing the ESD device's static charge discharge effectiveness. Existing aircraft ESD device layout design methods struggle to evaluate the static charge discharge effectiveness of multiple ESD devices on an aircraft. Summary of the Invention

[0003] The purpose of this invention is to provide a method for designing the layout of electrostatic dischargers for aircraft, which can achieve balanced discharge of multiple electrostatic dischargers or maximum discharge of deposited static electricity.

[0004] The technical solution adopted in this invention is an aircraft electrostatic discharger layout design method, comprising the following steps: Step 1: Calculate and obtain the total deposited electrostatic current of the aircraft; Step 2: Calculate the number of electrostatic dischargers that need to be installed on the aircraft based on the total deposited electrostatic current. Step 3: Conduct simulation of electrostatic distribution on the aircraft to determine the final electrostatic discharger placement area and number of areas; Step 4: Based on the number of electrostatic dischargers and the number of areas, formulate several preliminary layout schemes for the electrostatic dischargers of the entire machine; Step 5: Use the total discharge current I Q The maximum or balanced discharge of all electrostatic dischargers in the machine is used as the criterion to determine the layout design scheme of the electrostatic dischargers in the machine. Step 6: Evaluate the rationality of the overall electrostatic discharger layout scheme of the aircraft to obtain the final layout scheme of the overall electrostatic discharger of the aircraft.

[0005] The invention is further characterized by: Step 1 specifically involves calculating and obtaining the total deposited electrostatic current of the aircraft according to formula (1) or (2); I t = q p vc A eff (1); in,q p Stored charge of a single particle, unit: c / p; c Particle concentration per unit volume, unit: p / m 3 ; A eff The frontal surface area of ​​the aircraft, in meters (m²). 2 ; v The speed of the aircraft, in m / s; I t =I c ×A eff ×ν / 600 (2); in, I c Charging current density, unit: μA / m 2 ν represents flight speed, in knots. A eff The frontal surface area of ​​the aircraft, in meters (m²). 2 .

[0006] Step 2 specifically involves: based on the discharge index of a single electrostatic discharger. I q And the total static current deposited on the aircraft I t Calculate the number of electrostatic dischargers that need to be installed on the aircraft. N , N 1= I t / I q (3); N Take greater than N The smallest even number equal to 1.

[0007] Step 3 specifically involves: conducting an aircraft electrostatic distribution simulation. Based on the aircraft's electric field intensity distribution, the region with the largest electric field distribution at the aircraft's trailing edge is selected as the electrostatic discharger (ESD) placement area. Within this area, regions where the structural materials are unsuitable for ESD placement are excluded, as are areas where other airborne equipment has already been placed. The remaining areas represent the final ESD placement areas and the number of such areas. M .

[0008] Step 4 specifically involves: N One electrostatic discharger was assigned to M An area for scattering electrostatic dischargers, if N / MIf the value is greater than 2, then each electrostatic discharger placement area should preferentially place 2 electrostatic dischargers to form a variety of preliminary layout schemes for the entire machine's electrostatic dischargers.

[0009] Step 5 specifically involves: For each preliminary layout scheme of the electrostatic dischargers for the entire machine, taking the maximum number of electrostatic dischargers that can be arranged in one electrostatic discharger arrangement area within the preliminary layout scheme as... Q ; Place the first electrostatic discharger in each electrostatic discharger deployment area. L A The distance between the first electrostatic discharger and the tip of the structure. L A For values ​​greater than 100 mm, in the first... T The inner side of the electrostatic discharger is arranged with the first T +1 electrostatic discharger, L T For the first T The electrostatic discharger and the first T +1 spacing of electrostatic dischargers, L T For values ​​greater than 100mm, T =1, 2, ..., Q ; Simulation to obtain the steady-state electromotive force of the same aircraft V The discharge current of each electrostatic discharger I F Total discharge current I Q ,in F =1,2,…, N V is a value greater than 20kV; The total discharge current of the electrostatic discharger layout scheme of the whole machine I Q Using the maximum value as the criterion, a layout scheme for the electrostatic dischargers (ESDs) of the entire aircraft and the arrangement areas of each ESD are formed. L A and L T Configuration; Or the whole machine N Using equal discharge of individual electrostatic dischargers as the criterion, I F Standard deviation less than standard deviation limit P The overall electrostatic discharger layout scheme selects the total discharge current. I Q The largest overall electrostatic discharger (ESD) layout scheme for the entire aircraft, forming the overall ESD layout scheme and the arrangement areas of each ESD device. L A and LT Configuration.

[0010] Step 6 specifically involves: based on the aircraft-wide electrostatic discharger layout scheme determined in Step 5, simulating and obtaining the total deposited electrostatic current of the aircraft that satisfies the requirements of Step 1. I t aircraft steady-state electromotive force V Maximum discharge current of electrostatic discharger under steady-state potential of aircraft I Z According to the aircraft's steady-state electromotive force V and the maximum discharge current of the electrostatic discharger I Z The rationality of the overall electrostatic discharger (ESD) layout scheme of the aircraft was evaluated, and the final ESD layout scheme of the aircraft was obtained.

[0011] Step 6, specifically evaluating the rationality of the aircraft's overall electrostatic discharger layout, involves ensuring that the aircraft's steady-state electrostatic potential is met. V Less than or equal to 75kV ， Maximum discharge current of electrostatic discharger I Z Less than or equal to k* I q If k is a correction coefficient and k is greater than 1, then the overall electrostatic discharger layout scheme of the aircraft is reasonable and will be used as the final layout scheme for the overall electrostatic dischargers of the aircraft; if V >75kV or I Z >k* I q Then select the other aircraft-wide electrostatic discharger layout scheme from step 5 and repeat step 6 until... V Less than or equal to 75kV I Z Less than or equal to k* I q This led to the final layout scheme for the electrostatic dischargers across the entire aircraft.

[0012] The beneficial effects of this invention are: The aircraft electrostatic discharger (ESD) layout design method provided by this invention, based on electromagnetic modeling and simulation technology, performs quantitative simulation evaluation of various ESD layout schemes for aircraft ESDs, including the deposition of electrostatic discharge current and the steady-state potential of the deposited electrostatics. It optimizes the installation position of the ESDs and reduces the steady-state potential of the deposited electrostatics through balanced discharge design. This design method is agile, efficient, and accurate, strongly supporting the quantitative design and evaluation of various aircraft ESD protection systems. It can guide the ESD protection design of aircraft and the performance design of ESDs. This method is convenient and efficient, and has broad application prospects in the field of aircraft ESD protection design. Attached Figure Description

[0013] Figure 1 This is a flowchart illustrating the aircraft electrostatic discharger layout design method of the present invention. Figure 2 This is a diagram showing the isolation spacing configuration of the aircraft electrostatic discharger arrangement area according to the present invention. Detailed Implementation

[0014] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments.

[0015] Example 1 The aircraft electrostatic discharger layout design method proposed in this embodiment, such as Figure 1 As shown, it includes the following steps: Step 1: Calculate and obtain the total deposited electrostatic current of the aircraft; Step 2: Calculate the number of electrostatic dischargers that need to be installed on the aircraft based on the total deposited electrostatic current. Step 3: Conduct simulation of electrostatic distribution on the aircraft to determine the final electrostatic discharger placement area and number of areas; Step 4: Based on the number of electrostatic dischargers and the number of areas, formulate several preliminary layout schemes for the electrostatic dischargers of the entire machine; Step 5: Use the total discharge current I Q The maximum or balanced discharge of all electrostatic dischargers in the machine is used as the criterion to determine the layout design scheme of the electrostatic dischargers in the machine. Step 6: Evaluate the rationality of the overall electrostatic discharger layout scheme of the aircraft to obtain the final layout scheme of the overall electrostatic discharger of the aircraft.

[0016] Example 2 The aircraft electrostatic discharger layout design method proposed in this embodiment, such as Figure 1 As shown, it includes the following steps: Step 1: Calculate and obtain the total deposited electrostatic current of the aircraft; Specifically, the total electrostatic current deposited on the aircraft is calculated and obtained according to formula (1) or (2); I t = q p vc A eff (1); in, q p Stored charge of a single particle, unit: c / p; c Particle concentration per unit volume, unit: p / m 3 ; A eff The frontal surface area of ​​the aircraft, in meters (m²). 2 ; vThe speed of the aircraft, in m / s; I t =I c ×A eff ×ν / 600 (2); in, I c Charging current density, unit: μA / m 2 ν represents flight speed, in knots. A eff The frontal surface area of ​​the aircraft, in meters (m²). 2 ; Step 2: Calculate the number of electrostatic dischargers that need to be installed on the aircraft based on the total deposited electrostatic current. Step 3: Conduct simulation of electrostatic distribution on the aircraft to determine the final electrostatic discharger placement area and number of areas; Step 4: Based on the number of electrostatic dischargers and the number of areas, formulate several preliminary layout schemes for the electrostatic dischargers of the entire machine; Step 5: Use the total discharge current I Q The maximum or balanced discharge of all electrostatic dischargers in the machine is used as the criterion to determine the layout design scheme of the electrostatic dischargers in the machine. Step 6: Evaluate the rationality of the overall electrostatic discharger layout scheme of the aircraft to obtain the final layout scheme of the overall electrostatic discharger of the aircraft.

[0017] Example 3 The aircraft electrostatic discharger layout design method proposed in this embodiment, such as Figure 1 As shown, it includes the following steps: Step 1: Calculate and obtain the total deposited electrostatic current of the aircraft; Specifically, the total electrostatic current deposited on the aircraft is calculated and obtained according to formula (1) or (2); I t = q p vc A eff (1); in, q p Stored charge of a single particle, unit: c / p; c Particle concentration per unit volume, unit: p / m 3 ; A eff The frontal surface area of ​​the aircraft, in meters (m²). 2 ; v The speed of the aircraft, in m / s; I t =I c ×A eff ×ν / 600 (2); in, I c Charging current density, unit: μA / m 2 ν represents flight speed, in knots. A eff The frontal surface area of ​​the aircraft, in meters (m²). 2 ; Step 2: Calculate the number of electrostatic dischargers that need to be installed on the aircraft based on the total deposited electrostatic current. Specifically, based on the discharge index of a single electrostatic discharger... I q And the total static current deposited on the aircraft I t Calculate the number of electrostatic dischargers that need to be installed on the aircraft. N , N 1= I t / I q (3); N Take greater than N The smallest even number equal to 1; Step 3: Conduct simulation of electrostatic distribution on the aircraft to determine the final electrostatic discharger placement area and number of areas; Step 4: Based on the number of electrostatic dischargers and the number of areas, formulate several preliminary layout schemes for the electrostatic dischargers of the entire machine; Step 5: Use the total discharge current I Q The maximum or balanced discharge of all electrostatic dischargers in the machine is used as the criterion to determine the layout design scheme of the electrostatic dischargers in the machine. Step 6: Evaluate the rationality of the overall electrostatic discharger layout scheme of the aircraft to obtain the final layout scheme of the overall electrostatic discharger of the aircraft.

[0018] Example 4 The aircraft electrostatic discharger layout design method proposed in this embodiment, such as Figure 1 As shown, it includes the following steps: Step 1: Calculate and obtain the total deposited electrostatic current of the aircraft; Specifically, the total electrostatic current deposited on the aircraft is calculated and obtained according to formula (1) or (2); I t = qp vc A eff (1); in, q p Stored charge of a single particle, unit: c / p; c Particle concentration per unit volume, unit: p / m 3 ; A eff The frontal surface area of ​​the aircraft, in meters (m²). 2 ; v The speed of the aircraft, in m / s; I t =I c ×A eff ×ν / 600 (2); in, I c Charging current density, unit: μA / m 2 ν represents flight speed, in knots. A eff The frontal surface area of ​​the aircraft, in meters (m²). 2 ; Step 2: Calculate the number of electrostatic dischargers that need to be installed on the aircraft based on the total deposited electrostatic current. Specifically, based on the discharge index of a single electrostatic discharger... I q And the total static current deposited on the aircraft I t Calculate the number of electrostatic dischargers that need to be installed on the aircraft. N , N 1= I t / I q (3); N Take greater than N The smallest even number equal to 1; Step 3: Conduct simulation of electrostatic distribution on the aircraft to determine the final electrostatic discharger placement area and number of areas; Specifically, the process involves: conducting simulations of electrostatic distribution on the aircraft; selecting the region with the strongest electric field distribution at the aircraft's trailing edge as the electrostatic discharger (ESD) placement area based on the aircraft's electric field intensity distribution; excluding areas where the structural materials are unsuitable for ESD placement and areas already occupied by other airborne equipment; and determining the final ESD placement area and its number. M ; Step 4: Based on the number of electrostatic dischargers and the number of areas, formulate several preliminary layout schemes for the electrostatic dischargers of the entire machine; Step 5: Use the total discharge current I Q The maximum or balanced discharge of all electrostatic dischargers in the machine is used as the criterion to determine the layout design scheme of the electrostatic dischargers in the machine. Step 6: Evaluate the rationality of the overall electrostatic discharger layout scheme of the aircraft to obtain the final layout scheme of the overall electrostatic discharger of the aircraft.

[0019] Example 5 The aircraft electrostatic discharger layout design method proposed in this embodiment, such as Figure 1 As shown, it includes the following steps: Step 1: Calculate and obtain the total deposited electrostatic current of the aircraft; Specifically, the total electrostatic current deposited on the aircraft is calculated and obtained according to formula (1) or (2); I t = q p vc A eff (1); in, q p Stored charge of a single particle, unit: c / p; c Particle concentration per unit volume, unit: p / m 3 ; A eff The frontal surface area of ​​the aircraft, in meters (m²). 2 ; v The speed of the aircraft, in m / s; I t =I c ×A eff ×ν / 600 (2); in, I c Charging current density, unit: μA / m 2 ν represents flight speed, in knots. A eff The frontal surface area of ​​the aircraft, in meters (m²). 2 ; Step 2: Calculate the number of electrostatic dischargers that need to be installed on the aircraft based on the total deposited electrostatic current. Specifically, based on the discharge index of a single electrostatic discharger... I q And the total static current deposited on the aircraft It Calculate the number of electrostatic dischargers that need to be installed on the aircraft. N , N 1= I t / I q (3); N Take greater than N The smallest even number equal to 1; Step 3: Conduct simulation of electrostatic distribution on the aircraft to determine the final electrostatic discharger placement area and number of areas; Specifically, the process involves: conducting simulations of electrostatic distribution on the aircraft; selecting the region with the strongest electric field distribution at the aircraft's trailing edge as the electrostatic discharger (ESD) placement area based on the aircraft's electric field intensity distribution; excluding areas where the structural materials are unsuitable for ESD placement and areas already occupied by other airborne equipment; and determining the final ESD placement area and its number. M ; Step 4: Based on the number of electrostatic dischargers and the number of areas, formulate several preliminary layout schemes for the electrostatic dischargers of the entire machine; Specifically: N One electrostatic discharger was assigned to M An area for scattering electrostatic dischargers, if N / M If the value is >2, then each electrostatic discharger placement area should preferentially place 2 electrostatic dischargers to form a variety of preliminary layout schemes for the electrostatic dischargers of the whole machine. Step 5: Use the total discharge current I Q The maximum or balanced discharge of all electrostatic dischargers in the machine is used as the criterion to determine the layout design scheme of the electrostatic dischargers in the machine. Specifically, for each preliminary layout scheme of the electrostatic dischargers for the entire machine, the maximum number of electrostatic dischargers that can be arranged in one electrostatic discharger arrangement area within the preliminary layout scheme is taken as follows: Q ; Place the first electrostatic discharger in each electrostatic discharger deployment area. L A The distance between the first electrostatic discharger and the tip of the structure. L A For values ​​greater than 100 mm, in the first... T The inner side of the electrostatic discharger is arranged with the first T +1 electrostatic discharger, L T For the first T The electrostatic discharger and the first T +1 spacing of electrostatic dischargers, LT For values ​​greater than 100mm, T =1, 2, ..., Q ; Simulation to obtain the steady-state electromotive force of the same aircraft V The discharge current of each electrostatic discharger I F Total discharge current I Q ,in F =1,2,…, N V is a value greater than 20kV; The total discharge current of the electrostatic discharger layout scheme of the whole machine I Q Using the maximum value as the criterion, a layout scheme for the electrostatic dischargers (ESDs) of the entire aircraft and the arrangement areas of each ESD are formed. L A and L T Configuration; Or the whole machine N Using equal discharge of individual electrostatic dischargers as the criterion, I F Standard deviation less than standard deviation limit P The overall electrostatic discharger layout scheme selects the total discharge current. I Q The largest overall electrostatic discharger (ESD) layout scheme for the entire aircraft, forming the overall ESD layout scheme and the arrangement areas of each ESD device. L A and L T Configuration; Step 6: Evaluate the rationality of the overall electrostatic discharger layout scheme of the aircraft to obtain the final layout scheme of the overall electrostatic discharger of the aircraft. Specifically, based on the aircraft's overall electrostatic discharger layout scheme determined in step 5, simulation is used to obtain the total deposited electrostatic current of the aircraft that satisfies the requirements of step 1. I t aircraft steady-state electromotive force V Maximum discharge current of electrostatic discharger under steady-state potential of aircraft I Z According to the aircraft's steady-state electromotive force V and the maximum discharge current of the electrostatic discharger I Z The rationality of the overall electrostatic discharger layout scheme of the aircraft is evaluated, and the final layout scheme of the overall electrostatic discharger of the aircraft is obtained. The rationality of the overall electrostatic discharger layout scheme for the aircraft is specifically assessed by ensuring that it meets the aircraft's steady-state electromotive force. V Less than or equal to 75kV ， Maximum discharge current of electrostatic dischargerI Z Less than or equal to k* I q If k is a correction coefficient and k is greater than 1, then the overall electrostatic discharger layout scheme of the aircraft is reasonable and will be used as the final layout scheme for the overall electrostatic dischargers of the aircraft; if V >75kV or I Z >k* I q Then select the other aircraft-wide electrostatic discharger layout scheme from step 5 and repeat step 6 until... V Less than or equal to 75kV I Z Less than or equal to k* I q This led to the final layout scheme for the electrostatic dischargers across the entire aircraft.

[0020] Example 6 The aircraft electrostatic discharger layout design method proposed in this embodiment includes the following steps: Step 1: Calculate and obtain the total deposited electrostatic current of the aircraft; According to the formula in SAE ARP 5672-2009 "Aircraft Precipitation Static Certification" I t = q p vcA eff Alternatively, according to the formula in MIL-STD-464A, "Electromagnetic Environmental Effects Requirements For Systems". I t =I c ×A eff ×ν / 600 Calculate and obtain the total deposited electrostatic current of the aircraft. I t =500μA; Step 2: Calculate the number of electrostatic dischargers that need to be installed on the aircraft; Based on the discharge index of a single electrostatic discharger I q =50μA and the total electrostatic current deposited on the aircraft I t =500μA Calculate the number of electrostatic dischargers required for the aircraft N =10; Step 3: Conduct simulation of electrostatic distribution on the aircraft to determine the final electrostatic discharger placement area and number of areas; Simulations of electrostatic distribution deposition on an aircraft were conducted. Based on the electric field intensity distribution of the aircraft, the outer trailing edges of the wings and tail were selected as the areas for electrostatic discharger (ESD) placement. Considering the symmetry of the aircraft, the final ESD placement areas and the number of areas were determined. M =4.

[0021] Step 4: Formulate a variety of preliminary layout schemes for the electrostatic dischargers of the entire machine; Based on the number of aircraft electrostatic dischargers obtained in step 2 N =10 and the electrostatic discharger arrangement area in step 3 M =2, N / M Since 2.5 > 2, each electrostatic discharger (ESD) placement area should ideally have 2 ESDs, resulting in two ESD layout schemes for the entire aircraft. Scheme 1 has 3 ESDs on one wing and 2 on one tail. Scheme 2 has 2 ESDs on one wing and 3 on one tail. The maximum number of ESDs that can be placed in one ESD placement area within any of these layout schemes is taken as... Q =3.

[0022] Step 5, with the total discharge current I Q The maximum or balanced discharge of all electrostatic dischargers in the machine is used as the criterion to determine the layout design scheme of the electrostatic dischargers in the machine. like Figure 2 As shown, the first electrostatic discharger is placed in the wing or tail area. L A The distance between the first electrostatic discharger and the tip of the structure. L A =200mm, and the second electrostatic discharger is arranged inside the first electrostatic discharger. L 1 represents the distance between the first electrostatic discharger and the second electrostatic discharger. L 2 represents the distance between the second and third electrostatic dischargers. L 1 = 200m L 2 = 200m; Using the maximum discharge current in the wing area as the criterion, a system is formed. Q =Layout design scheme of 3 electrostatic dischargers, forming a series of L A and L T Value, of which L A =310mm 、L 1=300mL 2=400m; the maximum discharge current in the tail fin area is used as the criterion to form Q =Layout design scheme of 3 electrostatic dischargers, forming a series of L A and L T Value, of which L A =300mm 、L 1=350m L 2 = 400m; For each possible layout of the electrostatic dischargers across the entire aircraft, the steady-state electromotive force of the aircraft is obtained through simulation. V =Discharge current of each electrostatic discharger at 40kV I F Total discharge current I Q For the first type of all-machine electrostatic discharger layout scheme, I 1=59μA I 2=56μA I 3=53μA I 4=52μA I 5 = 49 μA I 6 = 47 μA I 7=54μA I 8 = 51 μA I 9 = 61 μA I 10 =62μA I Q =544μA; For the second overall electrostatic discharger layout scheme, I 1 = 53 μA I 2=52μA I 3=54μA I 4=52μA I 5 = 47 μA I 6=49μA I 7 = 51 μA I 8 = 47 μA I 9 = 48 μA I 10 =47μA I Q =500μA; The total discharge current of the electrostatic discharger layout scheme of the whole machine I Q Using the maximum value as the criterion, the first overall electrostatic discharger layout scheme is selected, with each electrostatic discharger placement area... L A and L TThe configuration is as follows, wing area L A =310mm 、L 1=300m L 2=400m, tail area L A =300mm 、L 1 = 350m; With the whole machine N Using equal discharge of individual electrostatic dischargers as the criterion, I F Standard deviation less than standard deviation limit P In the overall electrostatic discharger layout scheme with a current of 3, the total discharge current is selected. I Q The largest overall aircraft electrostatic discharger (ESD) layout scheme is selected as the second overall aircraft ESD layout scheme, with the ESDs arranged in various areas. L A and L T The configuration is as follows, wing area L A =310mm 、L 1=300m, tail area L A =300mm 、L 1=350m L 2 = 400m.

[0023] Step 6: Evaluate the rationality of the overall electrostatic discharger layout scheme for the aircraft to obtain the final layout scheme for the overall electrostatic dischargers of the aircraft.

[0024] According to the whole machine N The second aircraft-wide electrostatic discharger layout scheme, determined by the criterion of equal discharge from all electrostatic dischargers, is simulated to obtain the total deposited electrostatic current of the aircraft that satisfies step 1. I t Steady-state potential of aircraft = 500 μA V Maximum discharge current of electrostatic discharger under 40kV and aircraft steady-state potential. I Z =54μA; Obtained steady-state electric potential of the aircraft V =40kV and maximum discharge current of electrostatic discharger I Z =54μA to evaluate the rationality of the aircraft's overall electrostatic discharger layout scheme, and the aircraft's steady-state potential. V =40kV less than 75kV ， Maximum discharge current of electrostatic discharger I Z =54μA < k* Iq =55μA, k=1.1, the second layout scheme of the electrostatic discharger for the whole aircraft is selected as the final layout scheme of the electrostatic discharger for the whole aircraft.

Claims

1. A method for designing the layout of an aircraft electrostatic discharger, characterized in that, Includes the following steps: Step 1: Calculate and obtain the total deposited electrostatic current of the aircraft; Step 2: Calculate the number of electrostatic dischargers that need to be installed on the aircraft based on the total deposited electrostatic current. Step 3: Conduct simulation of electrostatic distribution on the aircraft to determine the final electrostatic discharger placement area and number of areas; Step 4: Based on the number of electrostatic dischargers and the number of areas, formulate several preliminary layout schemes for the electrostatic dischargers of the entire machine; Step 5: Use the total discharge current I Q The maximum or balanced discharge of all electrostatic dischargers in the machine is used as the criterion to determine the layout design scheme of the electrostatic dischargers in the machine. Step 6: Evaluate the rationality of the overall electrostatic discharger layout scheme of the aircraft to obtain the final layout scheme of the overall electrostatic discharger of the aircraft.

2. The aircraft electrostatic discharger layout design method according to claim 1, characterized in that, Step 1 specifically involves: calculating and obtaining the total electrostatic current deposited on the aircraft according to formula (1) or (2); I t = q p vc A eff （1）； in, q p Stored charge of a single particle, unit: c / p; c Particle concentration per unit volume, unit: p / m 3 ; A eff The frontal surface area of ​​the aircraft, in meters (m²). 2 ; v The speed of the aircraft, in m / s; I t =I c ×A eff ×ν / 600 （2）； in, I c Charging current density, unit: μA / m 2 ν represents flight speed, in knots. A eff The frontal surface area of ​​the aircraft, in meters (m²). 2 .

3. The aircraft electrostatic discharger layout design method according to claim 2, characterized in that, Step 2 specifically involves: based on the discharge index of a single electrostatic discharger... I q And the total electrostatic current deposited on the aircraft I t Calculate the number of electrostatic dischargers that need to be installed on the aircraft. N , N 1= I t / I q （3）； N Take greater than N The smallest even number equal to 1.

4. The aircraft electrostatic discharger layout design method according to claim 3, characterized in that, Step 3 specifically involves: conducting an electrostatic distribution simulation of the aircraft deposition; selecting the region with the largest electric field distribution at the aircraft's trailing edge as the electrostatic discharger (ESD) placement area based on the aircraft's electric field intensity distribution; excluding areas where the structural materials are unsuitable for ESD placement and areas where other airborne equipment has already been placed within the ESD placement area; and determining the remaining area as the final ESD placement area and the number of areas. M .

5. The aircraft electrostatic discharger layout design method according to claim 4, characterized in that, Step 4 specifically involves: [The text abruptly ends here, likely due to an incomplete sentence or a missing section.] N One electrostatic discharger was assigned to M An area for scattering electrostatic dischargers, if N / M If the value is greater than 2, then each electrostatic discharger placement area should preferentially place 2 electrostatic dischargers to form a variety of preliminary layout schemes for the entire machine's electrostatic dischargers.

6. The aircraft electrostatic discharger layout design method according to claim 2, characterized in that, Step 5 specifically involves: for each preliminary layout scheme of the electrostatic dischargers for the entire machine, taking the maximum number of electrostatic dischargers arranged in one electrostatic discharger arrangement area within the preliminary layout scheme as... Q ; Place the first electrostatic discharger in each electrostatic discharger deployment area. L A The distance between the first electrostatic discharger and the tip of the structure. L A For values ​​greater than 100 mm, in the first... T The inner side of the electrostatic discharger is arranged with the first T +1 electrostatic discharger, L T For the first T The electrostatic discharger and the first T +1 spacing of electrostatic dischargers, L T For values ​​greater than 100mm, T =1, 2, ..., Q ; Simulation to obtain the steady-state electromotive force of the same aircraft V The discharge current of each electrostatic discharger I F Total discharge current I Q ,in F =1,2,…, N V is a value greater than 20kV; The total discharge current of the electrostatic discharger layout scheme of the whole machine I Q Using the maximum value as the criterion, a layout scheme for the electrostatic dischargers (ESDs) of the entire aircraft and the arrangement areas of each ESD are formed. L A and L T Configuration; Or the whole machine N Using equal discharge of individual electrostatic dischargers as the criterion, I F Standard deviation less than the standard deviation limit P The overall electrostatic discharger layout scheme selects the total discharge current. I Q The largest overall electrostatic discharger (ESD) layout scheme for the entire aircraft, forming the overall ESD layout scheme and the arrangement areas of each ESD device. L A and L T Configuration.

7. The aircraft electrostatic discharger layout design method according to claim 6, characterized in that, Step 6 specifically involves: based on the aircraft-wide electrostatic discharger layout scheme determined in step 5, simulating and obtaining the total deposited electrostatic current of the aircraft that satisfies the requirements of step 1. I t aircraft steady-state electromotive force V Maximum discharge current of electrostatic discharger under steady-state potential of aircraft I Z According to the aircraft's steady-state electromotive force V and the maximum discharge current of the electrostatic discharger I Z The rationality of the overall electrostatic discharger (ESD) layout scheme of the aircraft was evaluated, and the final ESD layout scheme of the aircraft was obtained.

8. The aircraft electrostatic discharger layout design method according to claim 7, characterized in that, The evaluation of the rationality of the aircraft's overall electrostatic discharger layout scheme in step 6 specifically involves ensuring that the aircraft's steady-state electrostatic potential is met. V Less than or equal to 75kV ， Maximum discharge current of electrostatic discharger I Z Less than or equal to k* I q If k is a correction coefficient and k is greater than 1, then the overall electrostatic discharger layout scheme of the aircraft is reasonable and will be used as the final layout scheme for the overall electrostatic dischargers of the aircraft; if V >75kV or I Z >k* I q Then select the other aircraft-wide electrostatic discharger layout scheme from step 5 and repeat step 6 until... V Less than or equal to 75kV I Z Less than or equal to k* I q This led to the final layout scheme for the electrostatic dischargers across the entire aircraft.

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